Aircraft with counter-rotating turbofan engines

Patent metadata

Field	Value
Publication number	US-9878798-B2
Application number	US-201514964114-A
Country	US
Kind code	B2
Filing date	Dec 9, 2015
Priority date	Dec 31, 2014
Publication date	Jan 30, 2018
Grant date	Jan 30, 2018

Abstract

An aircraft including a frame, a first turbofan engine coupled to the frame, and a second turbofan engine coupled to the frame is disclosed. The first turbofan engine includes a first turbine, a first fan coupled to the first turbine to be driven by rotation of the first turbine, and a first transmission coupled between the first turbine and the first fan to transmit rotation from the first turbine to the first fan. The second turbofan engine includes a second turbine, a second fan coupled to the second turbine to be driven by rotation of the second turbine, and a second transmission coupled between the second turbine and the second fan to transmit rotation from the second turbine to the second fan.

First claim

What is claimed is:

1. An aircraft comprising
a frame,
a first turbofan engine coupled to the frame, the first turbofan engine including a first turbine, a first fan coupled to the first turbine to be driven by rotation of the first turbine, and a first transmission coupled between the first turbine and the first fan to transmit rotation from the first turbine to the first fan, the first transmission having a star gearset, and
a second turbofan engine coupled to the frame, the second turbofan engine including a second turbine, a second fan coupled to the second turbine to be driven by rotation of the second turbine, and a second transmission coupled between the second turbine and the second fan to transmit rotation from the second turbine to the second fan, the second transmission having a planetary gearset,
wherein the first turbine and the second turbine are configured to rotate in a first direction, the first transmission is configured to transmit rotation from the first turbine to the first fan to cause rotation of the first fan in the first direction, and the second transmission is configured to transmit rotation from the second turbine to the second fan to cause rotation of the second fan in a second direction opposite the first direction.

2. The aircraft of claim 1 , wherein the star gearset includes a sun gear coupled to the first turbine for rotation therewith, a plurality of planet gears intermeshed with the sun gear and mounted to a carrier grounded to a case, and a ring gear intermeshed with the plurality of planet gears and coupled to the first fan for rotation therewith.

3. The aircraft of claim 1 , wherein the planetary gearset includes a sun gear coupled to the second turbine for rotation therewith, a plurality of planet gears intermeshed with the sun gear and mounted to a carrier coupled to the second fan for rotation therewith, and a ring gear intermeshed with the plurality of planet gears and grounded to a case.

4. The aircraft of claim 3 , wherein the star gearset includes a sun gear coupled to the first turbine for rotation therewith, a plurality of planet gears intermeshed with the sun gear and mounted to a carrier grounded to a case, and a ring gear intermeshed with the plurality of planet gears and coupled to the first fan for rotation therewith.

5. The aircraft of claim 4 , wherein the first transmission is configured to provide a first speed ratio between the first turbine and the first fan, the second transmission is configured to provide a second speed ratio between the second turbine and the second fan, and a magnitude of the first speed ratio is equal to a magnitude of the second speed ratio.

6. The aircraft of claim 1 , wherein the first fan includes a fan disk and a plurality of fan blades coupled to the fan disk to establish a first pitch angle, the second fan includes a fan disk and a plurality of fan blades coupled to the fan disk to establish a second pitch angle, and the second pitch angle is about equal to and opposite the first pitch angle.

7. The aircraft of claim 6 , wherein the fan blades of the first fan are movable relative to the fan disk of the first fan to change the first pitch angle and the fan blades of the second fan are movable relative to the fan disk of the second fan to change the second pitch angle.

8. The aircraft of claim 6 , wherein the fan blades of the first fan are immovably coupled to the fan disk of the first fan and the fan blades of the second fan are immovably coupled to the fan disk of the second fan.

9. The aircraft of claim 1 , further comprising a fuselage arranged between the first turbofan engine and the second turbofan engine.

10. An engine set for an aircraft, the engine set comprising
a first turbofan engine including a first turbine, a first fan coupled to the first turbine to be driven by rotation of the first turbine, and a first transmission coupled between the first turbine and the first fan to transmit rotation from the first turbine to the first fan, the first transmission including a planetary gearset having a sun gear coupled to the first turbine for rotation therewith, a plurality of planet gears intermeshed with the sun gear and mounted to a carrier coupled to the first fan for rotation therewith, and a ring gear intermeshed with the plurality of planet gears and grounded to a case, and
a second turbofan engine including a second turbine, a second fan coupled to the second turbine to be driven by rotation of the second turbine, and a second transmission coupled between the second turbine and the second fan to transmit rotation from the second turbine to the second fan, the second transmission including a star gearset having a sun gear coupled to the second turbine for rotation therewith, a plurality of planet gears intermeshed with the sun gear and mounted to a carrier grounded to the case, and a ring gear intermeshed with the plurality of planet gears and coupled to the second fan for rotation therewith,
wherein the first turbine and the second turbine are configured to rotate in a first direction, the first transmission is configured to transmit rotation from the first turbine to the first fan to cause rotation of the first fan in the first direction, and the second transmission is configured to transmit rotation from the second turbine to the second fan to cause rotation of the second fan in a second direction opposite the first direction.

11. The engine set of claim 10 , wherein the first transmission is configured to provide a first speed ratio between the first turbine and the first fan, the second transmission is configured to provide a second speed ratio between the second turbine and the second fan, and a magnitude of the first speed ratio is equal to a magnitude of the second speed ratio.

12. The engine set of claim 11 , wherein (i) the sun gear of the first transmission has a number of gear teeth, (ii) the ring gear of the first transmission has a number of gear teeth, (iii) the sun gear of the second transmission has a number of gear teeth, (iv) the ring gear of the second transmission has a number of gear teeth, (v) the number of gear teeth of the sun gears of the respective first and second transmissions are different from one another, and (vi) the number of gear teeth of the ring gears of the respective first and second transmissions are different from one another.

13. The engine set of claim 11 , wherein the first fan includes a fan disk and a plurality of fan blades coupled to the fan disk to establish a first pitch angle, the second fan includes a fan disk and a plurality of fan blades coupled to the fan disk to establish a second pitch angle, and the second pitch angle is about equal to and opposite the first pitch angle.

14. A method of operating an aircraft, the method comprising
operating a first turbofan engine of the aircraft to cause a first transmission of the first turbofan engine including a star gearset to transmit rotation from a first turbine of the first turbofan engine to a first fan of the first turbofan engine to cause the first fan to rotate in a first direction,
operating a second turbofan engine of the aircraft to cause a second transmission of the second turbofan engine including a planetary gearset to transmit rotation from a second turbine of the second turbofan engine to a second fan of the second turbofan engine to cause the second fan to rotate in a second direction opposite the first direction, and
adjusting a first pitch angle of a first plurality of fan blades of the first fan relative to a second pitch angle of a second plurality of fan blades of the second fan when operating the first and second turbofan engines.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Nam Tech Inc

Inventors

• Cedoz Robert W

Classifications

• B64D35/02 Primary

  specially adapted for specific power plants · CPC title

• F02C3/107 Primary

  with two or more rotors connected by power transmission · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F01D1/26

  traversed by the working-fluid substantially axially · CPC title

• F01D7/00

  Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) · CPC title